EP2185346B1 - Compound contoured composite beams - Google Patents
Compound contoured composite beams Download PDFInfo
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- EP2185346B1 EP2185346B1 EP08797203.0A EP08797203A EP2185346B1 EP 2185346 B1 EP2185346 B1 EP 2185346B1 EP 08797203 A EP08797203 A EP 08797203A EP 2185346 B1 EP2185346 B1 EP 2185346B1
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- European Patent Office
- Prior art keywords
- flange
- longitudinal axis
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- plies
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Images
Classifications
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- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
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- B—PERFORMING OPERATIONS; TRANSPORTING
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Definitions
- a compound contour While a specific example of a compound contour is illustrated in the figures, it is to be appreciated that other shapes of compound contours are possible would also benefit from the techniques explained below that avoid wrinkling of the composite materials when constructing structural components, including but not limited floor beams. In other embodiments, it is not necessary that a compound contour have all of the features noted in the beam 104. That is, a contour can be a compound contour and not have both convex and concave radiuses, and a compound contour further does not necessarily require different straight portions that are angled, sloped or inclined relative to one another.
Description
- This disclosure relates generally to the manufacture of structural components using composite fiber lamination processes, and more specifically to the formation of composite fiber laminate structures having contoured profiles.
- The structural performance advantages of composites, such as, to name only a few, carbon fiber epoxy and graphite bismaleimide (BMI) materials, are widely known in the aerospace industry. Aircraft designers have been attracted to composites because of their superior stiffness, strength, and radar absorbing capabilities, for example. As more advanced materials and a wider variety of material forms have become available, aerospace usage of composites has increased. Automated tape layer technology has developed to become a widely used automated process for fabrication of large composite structures such as wing, without limitation, fuselage and empennage assemblies. Current composite fiber placement and tape laying technology has been improved to offer flexibility in process capabilities required for a wide variety of aerospace components. As composite lay-up processes improve with advances in automation new and innovative applications will be defined.
- The fabrication of certain components from composite materials, such as support beams, frames and stiffeners for aircraft or vehicles is desired for reduced weight and improved corrosion and fatigue resistant capabilities. Such components typically would be laid-up with plies of unidirectional carbon fiber composite materials, with plies oriented differently from one another depending on the structural properties desired.
- It has been observed, however, that some of the plies may wrinkle during the fabrication of certain components having non-uniform cross sections along the length of the part. This may result in the component having a varying, and discontinuous, outer contour or profile along its length. Such wrinkles are undesirable and have prevented widespread use and adoption of composite materials to fabricate components that may be prone to wrinkling of the composite materials.
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EP1151850 discloses a method for producing a stepped semi-hardened product having a joggle in an end portion and products produced by such a method. The process comprises: (1) laminating a plurality of fiber-reinforced composite sheets to each other by heating and cooling the sheets under pressure to provide a flat, plate-shaped laminate; (2) softening the plate-shaped laminate by heating and subsequently forming it into a particular shape using a forming tool whilst cooling it under pressure; and (3) heating an edge region under pressure to form a joggle. -
US2007/0175573 discloses thermoplastic composite parts formed of a collated plies which form a multi-layer stack. Multiple lay-ups may be cut from each stack for manufacturing the composite part. The lay-ups are pre-formed by bending and heating until an approximate shape of the finished part is obtained. - The present invention provides a structural component according to
claim 1. - Consistent with exemplary embodiments disclosed, components and fabrication methods are provided for the manufacture of structural components having discontinuities in their outer contour using composite material plies while avoiding undesirable wrinkling of some of the material plies used to fabricate the component.
- In an exemplary embodiment, a structural component is disclosed. The component comprises a body formed from unidirectional carbon fiber composite plies, the body having a longitudinal axis and a cross section perpendicular to the longitudinal axis. The cross section varies along a portion of the longitudinal axis to provide the body with at least one uniform contour and at least one compound contour. The composite plies forming the uniform contour are discontinuous along the longitudinal axis.
- The cross section may comprise a web and at least one flange extending from the web. The fiber composite plies may comprise unidirectional tape preimpregnated material. The body may comprise a beam having a web and opposing flanges extending from the web, a portion of the opposing flanges extending parallel to one another, and a portion of the flanges extending obliquely to one another to define the compound contour. One of the opposing webs may be substantially straight and continuous, and one of the flanges may be in part parallel and in part oblique to the other flange.
At least some of the composite plies forming the compound contour may be continuous along the longitudinal axis, thereby forming the compound contour profile without wrinkling of unidirectional fibers aligned with the longitudinal axis. The body may comprise multiple unidirectional carbon fiber composite plies arranged to define a linear profile and a non-linear profile, wherein the multiple plies forming the non-linear contoured profile are differently arranged from multiple plies forming the linear profile along the longitudinal axis of the component. The composite plies forming the fiber oriented parallel to the longitudinal axis may be discontinuous adjacent the non-linear contoured profile. The component may comprise an elongated beam. - An embodiment of a structural component fabricated from a composite material is also disclosed. The component comprises an elongated body formed from unidirectional carbon fiber composite plies, the body having a longitudinal axis and an axial length, an outer surface of the body being partly linear and partly non-linear along the axial length, and the plies having at least some fibers oriented parallel to the longitudinal axis. The fibers oriented parallel to the longitudinal axis are discontinuous along the non-linear outer surface, thereby avoiding wrinkling of the unidirectional fibers aligned with the longitudinal axis.
- The body comprises a web and at least one flange, the flange defining the non-linear part of the body. The plies may comprise unidirectional tape preimpregnated material, and the non-linear portion may comprise a straight portion extending obliquely to the longitudinal axis and at least one radius portion. The multiple plies forming the non-linear contoured profile may be differently arranged from the linear profile along the longitudinal axis of the component.
- Non-limiting and non-exhaustive embodiments are described with reference to the following Figures, wherein like reference numerals refer to like parts throughout the various views unless otherwise specified.
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Figure 1 is a flow diagram of aircraft production and service methodology. -
Figure 2 is a block diagram of an aircraft. -
Figure 3 is a cross sectional view of an aircraft illustrating an exemplary application of a structural component fabricated with composite materials. -
Figure 4 is a magnified view of a portion ofFigure 3 . -
Figure 5 is a perspective view of a portion of the component shown inFigures 3 and4 -
Figure 6 illustrates an exemplary charge lay-up and sequencing method for the manufacture of the component shown inFigure 5 . -
Figure 7 is an exploded view of the component illustrating its manufacture. - Exemplary embodiments of components and methods of manufacturing the components using composite materials are disclosed herein below that facilitate formation of components with certain contours to be formed without undesirable fiber wrinkles. The exemplary components and methods disclosed facilitate a more extensive and efficient use of, for example, unidirectional carbon fiber materials in the manufacturing of components having, for example, compound contours as described below, that until now have proven either too difficult or to expensive to repeatedly produce in an efficient and acceptable manner. The ability to form composite components in such contoured shapes presents significant advantages, including design considerations that may demand unusual shapes and jogs in the profile of the components, weight savings of a support structure by utilizing lighter weight materials to fabricate the components, and the development of high performance components engineered for specific use.
- In particular, the lighter weight composite materials used to form the components may achieve significant weight savings when utilized in combination to assemble a support structure or frame of, for example, an aircraft or other vehicle. Specifically for an aircraft construction having many support components, the potential weight savings can be substantial, leading to better fuel economy and reduced costs of operating the aircraft. Composite material components may also facilitate a reduction in maintenance costs.
- Referring more particularly to the drawings, embodiments of the disclosure may be described in the context of an aircraft manufacturing and
service method 50 as shown inFigure 1 and anaircraft 52 as shown inFigure 2 . During pre-production,exemplary method 50 may include specification anddesign 54 of theaircraft 52 andmaterial procurement 56. During production, component andsubassembly manufacturing 58 andsystem integration 60 of theaircraft 52 takes place. Thereafter, theaircraft 52 may go through certification anddelivery 62 in order to be placed inservice 64. While in service by a customer, theaircraft 52 is scheduled for routine maintenance and service 66 (which may also include modification, reconfiguration, refurbishment, and so on). - Each of the processes of
method 50 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limitation any number of venders, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on. - As shown in
Figure 2 , theaircraft 52 produced byexemplary method 50 may include anairframe 68 with a plurality ofsystems 70 and aninterior 72. Examples of high-level systems 70 include one or more of apropulsion system 74, anelectrical system 76, ahydraulic system 78, and anenvironmental system 80. Any number of other systems may be included. Although an aerospace example is shown, the principles of the invention may be applied to other industries, such as the automotive industry. - Apparatus and methods embodied herein may be employed during any one or more of the stages of the production and
service method 50. For example, components or subassemblies corresponding toproduction process 58 may be fabricated or manufactured in a manner similar to components or subassemblies produced while theaircraft 52 is in service. Also, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during the production stages 58 and 60, for example, by substantially expediting assembly of or reducing the cost of anaircraft 52. Similarly, one or more of apparatus embodiments, method embodiments, or a combination thereof may be utilized while theaircraft 52 is in service, for example and without limitation, to maintenance andservice 66. -
Figure 3 is a cross sectional view of anexemplary aircraft 100, that may correspond to theaircraft 52 ofFigure 2 that is the subject if themethod 50 ofFigure 1 , in which exemplary components and methods are to be explained. It is contemplated, however, that the benefits and advantages of the inventive component embodiments and formation methods described below may equally apply in other vehicle environments, such as automotive, truck, and recreational vehicles, as well as marine vehicles and non-vehicular applications such as buildings, towers, and other support structures. Generally speaking, the components and methods are applicable to any structural application wherein the benefits of composite material construction are desirable. The following discussion is therefore provided for purposes of illustration rather than limitation, and the components and methods disclosed herein are not intended to be restricted to any particular application, including but not limited to use in theaircraft 100, except when specifically defined as such in the appended claims. - As shown in
Figure 3 , theaircraft 100 includes afuselage 102 defining the outer body of theaircraft 100. A high performance,composite floor beam 104 is provided interior to thefuselage 102 and extends horizontally across an interior of thefuselage 102. Thefloor beam 104 serves as a structural component of theaircraft 100, andfloor panels 106 extend upon and are connected to thefloor beam 104 to provide apassenger compartment 108 above thefloor panels 106. In accordance with known aircraft, thepassenger compartment 108 is provided with seats and other amenities of modern aircraft for the safety, comfort, and convenience of travelers. In another embodiment, thecompartment 108 could alternatively serve as a cargo compartment or for other use than a passenger compartment. -
Stanchions 110 extend below thefloor beam 104 and at least in part define acargo compartment 112 beneath thefloor beam 104. Also in accordance with known aircraft, thecargo compartment 112 may be adapted for storage of, for example, travel bags, travel gear, luggage or other items belong to aircraft passengers. Alternatively, or in addition to such items, thecargo compartment 112 may also be adapted to store, contain and secure other cargo items independent of, and not belonging to, any particular passenger of the aircraft in use. Theaircraft 100 is amenable to civilian use predominately for transporting passengers and their personal goods from place to place, for military use in transporting personnel and equipment from location to location, or for commercial shipping and distribution of goods to different locations. - It should be understood that
many floor beams 104 are provided along the length of the aircraft in a plane extending into and out of the plane of the page ofFigure 3 .Larger aircraft 100 would require larger andlonger beams 104 and a greater number ofbeams 104 than would asmaller aircraft 100. Collectively, thebeams 104 provide structural support and framework for theaircraft 100. - Turning now to
Figure 4 , it is seen that thefloor beam 104 in an exemplary embodiment is formed in the shape of an elongated 1-shape having anupper flange 120,lower flange 122, and aweb 124 interconnecting the upper andlower flanges upper flange 120 is generally straight and continuous while thelower flange 122 is neither straight nor continuous along the full length of the beam. - As shown in
Figure 4 , thelower flange 122 includes afirst portion 126, asecond portion 128 and atransition portion 130 extending between the first andsecond portions first portion 126 is generally parallel to thefirst flange 120 and is spaced a first transverse distance H1, measured in a perpendicular direction from thefirst flange 120. Thesecond portion 128 also extends generally parallel to thefirst flange 120, and is spaced a distance H2, also measured in a perpendicular direction from thefirst flange 120, that is less than H1. In one example, H1 is about 7.5 inches, and H2 is about 5.6 inches. The lesser dimension H2 provides for an increased clearance underlying thelower flange 122 to accommodate, for example, and without limitation, cables orconduits 131 that are run under thefloor beam 104. While exemplary dimensions of H1 and H2 have been provided, they are by no means necessary, and it is appreciated that the values of H1 and H2 may vary in other embodiments. - Now considering the
lower flange 122 in further detail, thetransition portion 130 connects the first andsecond portions first flange 120, and thetransition portion 130 extends at an angle with respect to each of the first andsecond portions transition portion 130 extends obliquely to thefirst flange 120 and each of the first andsecond portions second flange 122 for a specified distance. At any given point along thetransition portion 130, an edge of the transition portion is spaced from thefirst flange 120, measured in a direction perpendicular from thefirst flange 120, at a third and variable distance H3 that is between the distance H1 and H2. That is, H3 is nearly equal to H1 where thetransition portion 130 abuts thefirst portion 122, and gradually decreases to a value approximately equal to H2 where thetransition portion 130 abuts thesecond portion 128. - The inflection points 132 and 134 connecting the
transition portion 130 to the first andsecond portions second flange 122 and thebeam 104 overall. In practice, theinflection points transition portion 130 to the first andsecond portions point 132 is a convex radius and the other radius atpoint 134 is a concave radius. - Following the contour of the
lower flange 122 from right to left inFigure 4 , thefirst portion 126 is generally straight, smooth and horizontal in its outer shape and contour until it meets the convex radius atpoint 132. After theconvex radius 132, theflange 122 in thetransition portion 130 again becomes straight and generally smooth but extends at an angle or incline with respect to thefirst portion 126 until thetransition portion 130 meets the concave radius at connectingpoint 134. After the radius atpoint 134, thelower flange 122 in theportion 128 again becomes generally straight, smooth, and horizontal. Collectively, theportions transition portion 130 render the contour of thelower flange 122 as neither straight nor smooth because of the discontinuities between the straight and curved portions at theinflection points - The
transition portion 130 in the illustrated embodiment is shaped so that thelower flange 122 makes an inward jog to reduce the height profile of thebeam 104 and may provide increased clearance for the cables orconduits 131, or a greater height of theweb 124 where needed. The joggle may allow placement of the cables andconduits 131 in a more compact arrangement relative to thebeam 104, without significantly impacting the use of space above or below thebeam 104. In the context of a floor beam, this arrangement is sometimes referred to as a "joggle" that presents particular manufacturing challenges to formation of thebeam 104 using composite materials. Referring back toFigure 3 for a moment, thebeam 104 may have more than onetransition portion 130 forming more than one joggle along the length of the beam to provide a relatively large span of beam having an increased clearance for running cables and conduit, or for accommodating other mechanical and electrical components of the aircraft. - It has been observed that when attempting to construct the
beam 104 from plies of unidirectional carbon fiber composite materials, it has been observed that some of the plies of material may wrinkle along thelower flange 122 in the region of thetransition portion 130. As mentioned, such wrinkles may be undesirable, and efforts to reliably construct acceptable beams with composite materials in a cost effective manner have generally proven unsuccessful until the inventive beam and methods for fabricating the same were discovered and developed. -
Figure 5 illustrates a portion of a C-shapedchannel charge 142 used to fabricate thebeam 104. As is believed to be evident fromFigure 4 , two C-shaped channel charges 142 may be assembled back-to-back and secured to one another to form, for example, the I-shapedbeam 104. Thecharge 142 is shown in perspective view inFigure 5 wherein the manufacturing issues are perhaps a bit more evident. As previously explained, the beam construction, including theflanges web 124 in a C-shaped channel arrangement. Theflanges web 124. Thebeam 104 is generally elongated and has alongitudinal axis 140. Thefirst flange 120 in the exemplary embodiment may be generally straight and continuous and may extend parallel to thelongitudinal axis 140. The first andsecond portions first flange 120 and to one another, but are spaced at different distances from thefirst flange 120 as previously described. Theweb 124 is also generally planar and extends parallel to thelongitudinal axis 140. As is evident fromFigure 5 , however, thetransition portion 130 and the radius of therespective inflection points longitudinal axis 140. - In the
second flange 122, the combination of thestraight portions radiused portions transition portion 130, is one example of what is sometimes referred to as a compound contour. Thetransition portion 130 in the illustrated embodiment is partly rounded at theinflection points - While a specific example of a compound contour is illustrated in the figures, it is to be appreciated that other shapes of compound contours are possible would also benefit from the techniques explained below that avoid wrinkling of the composite materials when constructing structural components, including but not limited floor beams. In other embodiments, it is not necessary that a compound contour have all of the features noted in the
beam 104. That is, a contour can be a compound contour and not have both convex and concave radiuses, and a compound contour further does not necessarily require different straight portions that are angled, sloped or inclined relative to one another. - As used herein, the term "compound contour" shall broadly refer to any shape or outer surface profile that includes one or more significant changes and associated inconsistency in its outer shape and profile, exclusive of surface openings, indentations and the like for attaching the component to a structure, or for attaching other structures to the component. That is, as used herein the "profile" refers to the overall shape of the component as a whole, that may generally not be dependent on or affected by openings or other attachment features for mounting of the component in a specified location. The changes and inconsistency in the outer shape and profile of the component forming a compound contour may be characterized by a combination of intersecting surfaces of different character that may be discretely identifiable from one another. Different character of adjoining or intersecting surfaces may be identifiable by the presence of one or more inflection points, one or more rounded surfaces, different types of curved surfaces such as convex and concave surfaces, one or more curvatures having different centers and radius, straight portions that are differently sloped relative to one another, abrupt changes in the outer profile, and combinations thereof. "Compound contours" are specifically distinguished from simple contours, examples of which include, but are not limited to, a component that is uniformly tapered along its entire length, a component that is uniformly curved along its entire length, and a component that has a uniform or unchanging contour along its entire length.
- As a result of the compound contour of the
beam 104 in the illustrated embodiment, the cross section of thebeam 104, taken in a plane perpendicular to thelongitudinal axis 140, is not uniform along the length of the beam. Portions of the beam having a constant or continuous cross sectional are sometimes referred to as linear portions of thebeam 104, while the transition portion of the beam is sometimes referred to as a non-linear portion of thebeam 104 by virtue of its changing or variable cross section and outer shape along the length of thebeam 104. - Wrinkling of the composite material plies when attempting to construct such a contoured structural component as the
beam 104 using conventional composite fabrication processes laying-up different plies of composite material is believed to lie in composite material plies having the structural fibers arranged to be oriented with thelongitudinal axis 140 along the length of thebeam 104. Particularly, and because of the shape of thelower flange 122 having thetransition portion 130, the fibers that are oriented along and generally parallel to thelongitudinal axis 140 in thestraight portions transition portion 130 is shaped, causing some of the fibers to compress and bow or buckle and create the wrinkles. Such bowing of the fibers may also cause wrinkles in other adjacent composite material plies wherein the structural fibers are not aligned with thelongitudinal axis 140, such as plies wherein the structural fibers are oriented at, for example, 45° and 90° angles to thelongitudinal axis 140. It has been observed, for example, that when constructing the shape ofchannel charge 142 illustrated inFigure 5 with a lay-up of composite material plies, plies with fibers oriented plus 45°, 90° and -45° measured from thelongitudinal axis 140 do not tend to create wrinkles in thelower flange 122 unless 0° plies or plies having fibers extending parallel to thelongitudinal axis 140, are also present. - In recognition of this issue with the longitudinally extending fibers extending at a 0° angle from the longitudinal axis 140 (i.e., parallel to the longitudinal axis), the
beam 104, unlike conventional fabrication techniques that produce wrinkles, is fabricated using different ply orientations for the various portions of thebeam 104, and notably does not involve the bending of fibers oriented along thelongitudinal axis 140 to produce the compound contour. Rather, the plies having fibers oriented parallel to the longitudinal axis are cut so that they are discontinuous along the contoured edges of theweb 124 andflange 122 over the length of the part. The material plies that would otherwise result in compression of the fibers oriented along thelongitudinal axis 140 are separated out from the component construction and these plies are placed independently from the other plies having fibers oriented differently along the longitudinal axis to form the contoured flange. As a result of the discontinuous nature of the fibers oriented parallel to thelongitudinal axis 140, and also separate application of those fibers to the contoured portions of thebeam 104, none of those fibers are placed in compression during fabrication of thebeam 104, thus avoiding wrinkles in the formed component. - Still further, a unique approach is taken during the lay-up of flat charges used to form the
beam 104. In one embodiment, for example, the flat charges are grouped as much as possible into discrete stacks of either 0° plies with fibers extending parallel to thelongitudinal axis 140, or plies having fibers oriented at +45°, 90° and -45° with respect to the longitudinal axis. That is, the approach involves sequencing of a lay-up to create discrete ply groups consisting of 0° plies and groups of +45°, 90° and -45° plies. The 0° ply groups are separated into discrete web and flange elements along the contoured portion of thechannel charge 142. In particular, the 0° plies used to fabricate the contoured flange elements are not draped along with the plies to form the other elements of thecharge 142, but rather are linearly placed along the length of the part by hand or machine. This avoids the wrinkles that would occur if the 0° contoured flange elements were integral with the other lay-up elements. - An exemplary machine that is suitable for laying-up of the plies is disclosed in commonly owned
U.S. Patent No. 7,188,370 . It is believed that this machine and other machines are familiar to those in the art of fabrication of components using composite materials and that detailed discussion of the machines is generally beyond the scope of this disclosure. Further detail and explanation thereof are not believed to be necessary for those skilled in the art. In other embodiments, it is contemplated that the charges may be laid up manually. -
Figures 6 and7 illustrate further details of thecharge 142 and an exemplary charge lay-up and a method of sequencing composite charges for fabricating the C-shapedchannel charge 142 from, for example, unidirectional tape preimpregnated material, and more specifically, "Style 108" resin impregnated fiberglass fabric material plies. The method involves various plies having fibers stacked and sequenced to be oriented differently with respect to one another, and separately applying some of the plies to the linear and non-linear portions of the component. References to degrees in connection with the plies in the following discussion shall be understood to refer to the relative orientation of the fibers of the plies with respect to theaxis 140 of the C-shapedchannel charge 142. As such, a zero degree ply would have its fibers oriented parallel to the longitudinal axis. Also, as shown inFigure 5 , the charge drapes may be laid up and assembled using a lay-upmandrel 158 having the desired shape of the component to be fabricated. - For example, and considering the C-shaped
channel charge 142 shown inFigure 5 , and also referring toFigures 6 and7 , afirst drape charge 150 may be prepared in a first drape operation wherein one plus 45 degree oriented layer, a 90 degree layer, and one minus 45 degree layer are laid flat and draped over themandrel 158 to form part of thefirst flange 120, thesecond flange 122 and theweb 124. - In a second drape operation, two zero degree plies 152 and 153 are separately laid on the
web 124 and thecountoured flange 122. One of the zero degree plies 152 covers theweb 124 and thestraight flange 120. The other of the zero degree plies 153 covers the contouredflange 122. - While the zero
degree ply 152 covering theweb 124 and thestraight flange 120 is illustrated as part of the second drape operation inFigure 6 , it is understood that the may the zerodegree ply 152 may alternatively be combined and formed simultaneously with thedrape charge 150 of the first drape operation. In such an embodiment, however, the zerodegree ply 153 would still be separately laid in the separate drape operation. - In a third drape operation, one plus 45 degree layer and one minus 45
degree layer 154 are laid flat and draped over the layers of the first and second drape operation. That is the layers of the third drape operation form part of thefirst flange 120, thesecond flange 122 and theweb 124. - In a fourth drape operation, a zero
degree ply 156 and a zerodegree ply 157 are separately laid on theweb 124, thestraight flange 122 and the contouredflange 122. Theply 156 covers theweb 124 and thestraight flange 120, and theply 157 covers the contouredflange 122. - While the zero
degree ply 156 covering theweb 124 and thestraight flange 120 is illustrated as part of the fourth drape operation inFigure 6 , it is understood that the zerodegree ply 156 may alternatively be combined and formed simultaneously with thedrape charge 154 of the third drape operation. In such an embodiment, however, the zerodegree ply 157 would still be separately laid in the separate drape operation. - After the channel charge drape operations have been completed, the
charge 142 is ready for assembly to produce, for example thefloor beam 104 described inFigures 3 and4 . - While one example of the charge lay-up and method of sequencing plies having fibers oriented at plus and minus 45° and 90°, in addition to the zero degree plies, it is to be appreciated that the non-zero plies do not have to be oriented at plus or minus 45° and/or 90° in other embodiments. Other angles of fibers may likewise be utilized to meet particular needs and desires for forming components and for meeting particular objectives. It is also contemplated that in some embodiments certain of the plies, such as the 90° plies discussed above, may be considered optional.
- Using the above-described methodology, structural components such as the
beam 104, or other beams, stiffeners or other structural components having significant compound contour and surface discontinuities, may therefore be efficiently fabricated from unidirectional carbon fiber composite materials. More extensive and efficient use of unidirectional carbon fiber materials to fabricate components having contoured shapes without unacceptable wrinkling of the composite plies is facilitated, and appreciable weight savings may be realized when the components such as thebeams 104 are assembled into a larger structure. - While an
exemplary beam 104 and C-shapedcharge 142 having exemplary shapes have been described, it is to be understood that other components having other shapes and cross sections may likewise be formed while avoiding issues associated with wrinkling of the plies. Any component having a web and one or more flanges arranged in any shape may be benefit from the above-described methodology. For example, and without limitation, in addition to the I-shapedbeam 104 described above, similar techniques could be used to form contours in a J-shaped component having a compound contour, an L-shaped component having a single contoured flange extending from a web, a T-shaped component having at least one portion with a compound contour, and a Z-shaped component having at a least portion thereof with a compound contour. As still further non-limiting examples, components having a cross section shape resembling a number, such as the number "7" may be formed. Still other shapes are possible that are not reminiscent of the shapes of letters and numbers, including but-not limited to top-hat shapes and other shapes and cross sections. Moreover, combinations of such exemplary shapes of components may be assembled to form still other shapes, such as the C-shaped channels described above that are used to produce an I-shaped beam. - Likewise, such techniques may be utilized to form tubular elements (rectangular and square) with contours that may otherwise result in wrinkled composite materials. While the exemplary embodiments illustrated herein include one straight flange and one contoured flange, it is understood that in further and/or alternative embodiments, more than one contoured flange may be manufactured in the same component using the methods and techniques discussed above. That is, components having multiple contoured flanges could be formed into a vast number of desired shapes to produce components without undesirable wrinkling.
- Also, while the component embodiments and methods of fabricating them have thus far been disclosed in the context of a floor beam, other structural components may also be fabricated that avoid similar problems and offer similar advantages. That is, beams for other purposes may equally benefit from the techniques disclosed herein, as well as non-beam components that provide structural strength and support to an assembly of components collectively defining a larger structure.
- While the disclosed components and methods have been described in terms of various specific embodiments, those skilled in the art will recognize that the components and methods can be practiced with modification within the scope of the claims.
Claims (8)
- A structural component comprising:a body comprising unidirectional carbon fiber composite plies (152,153,156,157), the body having a longitudinal axis and a cross section perpendicular to the longitudinal axis, the cross section varying along a portion of the longitudinal axis to provide the body with at least one uniform contour and at least one compound contour;wherein the body comprises a beam (104) having a web (124) and at least one flange (122) extending from the web, a portion of the at least one flange extending parallel to the longitudinal axis, and a portion of the at least one flange extending obliquely to the longitudinal axis to define the compound contour; characterised in that:the composite plies having fibers oriented parallel to the longitudinal axis are discontinuous along the contoured edges of the web and flange over the length of the body.
- The component of claim 1, wherein the fiber composite plies (152,153,156,157) comprise unidirectional preimpregnated tape material.
- The component of claim 1, further comprising an opposing flange (120), said opposing flange opposing the at least one flange and extending from the web, wherein the portion of the at least one flange extending parallel to the longitudinal axis extends parallel to the opposing flange, and wherein the portion of the at least one flange extending obliquely to the longitudinal axis extends obliquely to the opposing flange.
- The component of claim 3, wherein the opposing flange (120) is substantially straight and continuous.
- The component of claim 3, wherein the at least one flange (122) is in part parallel and in part oblique to the opposing flange (120).
- The component of claim 1, wherein at least some of the composite plies (152,153,156,157) forming the at least one flange are continuous along the longitudinal axis, thereby forming the surface profile of the at least one flange without wrinkling of unidirectional fibers aligned with the longitudinal axis.
- The component of claim 1, wherein the at least one flange comprises:a first straight portion (126) having a first and uniform cross section along the longitudinal axis;a second straight portion (128) having a second and uniform cross section along the longitudinal axis, the second cross section being different from the first cross section; anda transition portion (130) extending between the first and second straight portions having a third cross section that is not uniform along the longitudinal axis.
- The component of claim 1, wherein the body comprises multiple unidirectional carbon fiber composite plies (152,153,156,157), wherein the fibers in the multiple plies are oriented differently from one another.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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EP20120172778 EP2502734B1 (en) | 2007-08-07 | 2008-08-05 | Method of fabricating a compound contoured composite beam |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US11/835,202 US7968169B2 (en) | 2007-08-07 | 2007-08-07 | Compound contoured composite beams and fabrication methods |
PCT/US2008/072233 WO2009020971A2 (en) | 2007-08-07 | 2008-08-05 | Compound contoured composite beams and fabrication methods |
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EP20120172778 Division EP2502734B1 (en) | 2007-08-07 | 2008-08-05 | Method of fabricating a compound contoured composite beam |
EP20120172778 Division-Into EP2502734B1 (en) | 2007-08-07 | 2008-08-05 | Method of fabricating a compound contoured composite beam |
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EP2185346A2 EP2185346A2 (en) | 2010-05-19 |
EP2185346B1 true EP2185346B1 (en) | 2016-05-04 |
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GB201006257D0 (en) * | 2010-04-15 | 2010-06-02 | Airbus Operations Ltd | Composite structure |
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US9701067B2 (en) | 2010-11-12 | 2017-07-11 | The Boeing Company | Method of laying up prepreg plies on contoured tools using a deformable carrier film |
EP2691776A4 (en) * | 2011-03-27 | 2015-04-15 | Oncostem Diagnostics Mauritius Pvt Ltd | Markers for identifying tumor cells, methods and kit thereof |
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US9090043B2 (en) | 2011-08-03 | 2015-07-28 | The Boeing Company | Molybdenum composite hybrid laminates and methods |
US8993097B2 (en) * | 2011-10-10 | 2015-03-31 | The Boeing Company | Tapered height curved composite stringers and corresponding panels |
US9327470B1 (en) * | 2012-12-05 | 2016-05-03 | The Boeing Company | Variable-radius laminated radius filler and system and method for manufacturing same |
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US20160009368A1 (en) * | 2013-02-28 | 2016-01-14 | The Boeing Company | Composite laminated plate having reduced crossply angle |
JP5959558B2 (en) * | 2014-03-13 | 2016-08-02 | アイシン高丘株式会社 | Composite structure and method for producing the same |
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GB9828368D0 (en) * | 1998-12-22 | 1999-02-17 | British Aerospace | Forming reinforcing components |
EP1250381A2 (en) * | 2000-01-13 | 2002-10-23 | Fulcrum Composites, Inc. | Process for in-line forming of pultruded composites |
JP4425424B2 (en) | 2000-05-01 | 2010-03-03 | 本田技研工業株式会社 | Method for producing semi-cured article with joggle made of fiber reinforced composite material, and method for producing preformed structure using the same |
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CN101772408B (en) | 2013-07-24 |
US20090041974A1 (en) | 2009-02-12 |
US7968169B2 (en) | 2011-06-28 |
WO2009020971A2 (en) | 2009-02-12 |
ES2585938T3 (en) | 2016-10-10 |
JP2010535653A (en) | 2010-11-25 |
CN101772408A (en) | 2010-07-07 |
WO2009020971A3 (en) | 2009-12-10 |
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